The Quasioptimal Flight of Spacecraft with a Solar Sail between Circular Geliocentric Orbits

The quasioptimal trajectory of the spacecraft with a solar sail quickest flight between two coplanar heliocentric circular orbits was constructed analytically in the approximate form. The trajectory is formed with the segment of logarithmic spiral and the segments of conjugation of a spiral with initial and end orbits. On each segment the angle between the solar plane and SC heliocentric radius vector is constant. The comparison of the constructed quasi optimal trajectory with the optimal one found as a result of numerical solving boundary-value problem of Pontrjagin maximum principle was made.